EASA AD No.: 2015-0056

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2015-0056 

Date: 31 March 2015 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation 

(EC) No 216/2008 on behalf of the European Community, its Member States and of the 

European third countries that participate in the activities of EASA under Article 66 of that 

Regulation.

This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an 

aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EU 

1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Design Approval Holder’s Name: 

ROLLS-ROYCE DEUTSCHLAND Ltd & Co KG 

Type/Model designation(s): 

Tay 650 and Tay 651 engines

TCDS Number: EASA.E.063 

Foreign AD: Not applicable 

Supersedure: This AD supersedes EASA AD 2007-0086 dated 30 March 2007. 

ATA 72 Engine – High Pressure Turbine Stage 1 Disc – Cyclic Life Limit 

Reduction 

Manufacturer(s): Rolls-Royce plc 

Applicability: Tay 650-15 and Tay 651-54 engines, all variants, all serial numbers. 

These engines are known to be installed on, but not limited to, Fokker F28 

Mark 0100 and Boeing 727 series aeroplanes. 

Reason: A recent analysis identified the need to reduce the existing cyclic life limit of 

certain High Pressure Turbine (HPT) Stage 1 discs, Part Number (P/N) 

JR32013, as compared with the values published in RRD Tay 650 and Tay 651 

engine Time Limit Manuals (TLM), Chapter 05-10-01. 

Operation of the affected HPT Stage 1 disc P/N JR32013 beyond the reduced 

cyclic life limit would likely result in an unsafe condition. 

This condition, if not corrected, could lead to part failure, possibly resulting in 

release of high energy debris with consequent damage to the aeroplane and/or 

injury to the occupants. 

Prompted by the analysis results, RRD issued Alert Non Modification Service 

Bulletin (NMSB) TAY-72-A1821 to inform about the reduced cyclic life limits for 

various affected flight plans. 

For the reasons described above, this AD requires implementation of the 

reduced cyclic life limits, as applicable to the various flight plans and 

replacement of HPT Stage 1 disc P/N JR32013 that have already exceeded the 

reduced cyclic life limit. 
EASA AD No.: 2015-0056

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Effective Date: 14 April 2015 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

For engines with a HPT Stage 1 disc P/N JR32013 installed, before exceeding 

the cyclic life limit as indicated in Table 1 of this AD, depending on flight plan 

the engine is operated in, as applicable, or within 100 flight cycles (FC) after the 

effective date of this AD, whichever occurs later, replace the HPT disc P/N 

JR32013 with a serviceable part in accordance with the instructions of RRD 

NMSB TAY-72-A1821. 

Table 1 HPT Stage 1 disc P/N JR32013 Life Limitation 

Engine Model Flight Plan Life Limit 

Tay 650-15 

A 18 900 FC 

B 15 500 FC 

C 11 500 FC 

D 9 300 FC 

Tay 651-54 N/A 10 873 FC 

 

Ref. Publications: RRD NMSB TAY-72-A1821 Revision 01 dated 26 March 2015. 

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD. 

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. This AD was posted on 02 February 2015 as PAD 15-008 for consultation 

until 02 March 2015. The Comment Response Document can be found at 

http://ad.easa.europa.eu. 

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu. 

4. For any question concerning the technical content of the requirements in 

this AD, please contact: 

Rolls-Royce Deutschland Ltd & Co KG 

Eschenweg 11,D-15827 Blankenfelde-Mahlow, Germany 

Telephone: +49 (0) 33 7086 1768, Fax +49 (0) 33 7086 3356 

E-mail: RRDTechnicalHelpdesk@Rolls-Royce.com.